CN112611485A - Method for determining linearity of parachute opening force sensor - Google Patents
Method for determining linearity of parachute opening force sensor Download PDFInfo
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- CN112611485A CN112611485A CN202011363385.XA CN202011363385A CN112611485A CN 112611485 A CN112611485 A CN 112611485A CN 202011363385 A CN202011363385 A CN 202011363385A CN 112611485 A CN112611485 A CN 112611485A
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000004364 calculation method Methods 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 claims abstract description 5
- 239000000126 substance Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 abstract description 2
- 230000035945 sensitivity Effects 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
- G01L1/16—Measuring force or stress, in general using properties of piezoelectric devices
Abstract
The invention discloses a method for determining the linearity of a parachute opening force sensor, which comprises the following steps: 1) obtain parachute opening force sensor's calibration data, include: measured force value xiAnd electrical output yi(ii) a 2) Calculating the following parameters according to the calibration test data; 3) determining a fitting linear equation of the parachute force cell according to the parameters; 4) each input value xiSubstituting the fitting linear equation in the step 3) to obtain numerical values of all points of a theoretical fitting linear line, and sequentially finding out the deviation between the calibration data value and the corresponding point value of the theoretical fitting linear line to obtain the maximum deviation; 5) and completing linear calculation according to the maximum deviation and the full range of the sensor. The invention provides a calculation method for improving the measurement accuracy and the output sensitivity of a force sensor, which ensures the normal and reliable work of a system where the force sensor is positioned and improves the overall accuracy of the system where the force sensor is positioned.
Description
Technical Field
The invention relates to a force sensor testing technology, in particular to a method for determining the linearity of a parachute opening force sensor of a parachute.
Background
The parachute opening force sensor is a complete force measuring device, and can convert the magnitude of the measured force into useful electric quantity output with a determined corresponding relation with the measured force to meet the requirement of process control, but the output electric quantity of the actual parachute opening force sensor cannot reflect the change of the measured force value, and a certain error always exists, so that the magnitude of the nonlinear error is required to measure the precision of the force sensor, the theoretical linearity also called absolute linearity is used at present, usually, 0% of zero point is taken as the starting point of a theoretical straight line, 100% of full-scale output is taken as the ending point, and the connecting line of the two points is the theoretical straight line. The nonlinear error of the fitted straight line is large, and the output precision of the parachute opening force sensor is reduced.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for determining the linearity of a parachute opening force sensor aiming at the defects in the prior art.
The technical scheme adopted by the invention for solving the technical problems is as follows: a method for determining the linearity of a parachute opening force sensor comprises the following steps:
1) obtain parachute opening force sensor's calibration data, include: measured force value xiAnd electrical output yi(ii) a Wherein i is 1,2,3, … …, n;
2) the following parameters were calculated from the calibration test data:
∑xi＝x1+x2+…+xn；
∑yi＝y1+y2+...+yn；
∑xiyi＝x1y1+x2y2+...+xnyn；
∑x2 i＝x1 2+x2 2+x3 2+...+xn 2；
3) determining a fitted linear equation for a parachute force cell from the parameters
y＝kx+b；
Wherein the content of the first and second substances,
4) each input value xiSubstituting the fitting linear equation in the step 3) to obtain numerical values of all points of a theoretical fitting linear line, and sequentially finding out the deviation between the calibration data value and the corresponding point value of the theoretical fitting linear line to obtain the maximum deviation;
5) and completing linear calculation according to the maximum deviation and the full range of the sensor.
According to the scheme, in the step 1), n is more than or equal to 40.
The invention has the following beneficial effects:
the invention provides a calculation method for improving the measurement precision and the output sensitivity of a force sensor, which utilizes calibration data to comprehensively obtain a fitting straight line of the force sensor. The method can also be used for calculating the linearity of other types of sensors (using force sensors such as lifesaving umbrellas, drag umbrellas, delivery umbrellas and the like), the accuracy of the sensors is improved, and the social benefit is remarkable.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a flow chart of a method of an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1, a method for determining the linearity of a parachute opening force sensor comprises the following steps:
1) obtain parachute opening force sensor's calibration data, include: measured force value xiAnd electrical output yi(ii) a Wherein i is 1,2,3, … …, n; (generally n.gtoreq.40)
2) The following parameters were calculated from the calibration test data:
∑xi＝x1+x2+...+xn；
∑yi＝y1+y2+...+yn；
∑xiyi＝x1y1+x2y2+...+xnyn；
∑x2 i＝x1 2+x2 2+x3 2+...+xn 2；
3) determining a fitted linear equation for a parachute force cell from the parameters
y＝kx+b；
Wherein the content of the first and second substances,
4) each input value xiSubstituting the fitting linear equation in the step 3) to obtain numerical values of all points of a theoretical fitting linear line, and sequentially finding out the deviation between the calibration data value and the corresponding point value of the theoretical fitting linear line to obtain the maximum deviation;
5) and completing linear calculation according to the maximum deviation and the full range of the sensor.
The following example uses least squares normalcy to solve a fitted line equation for a parachute load cell, for example: calibration data for a 50KN strain sensor are shown in Table 1
In order to find the fitted line equation, the sum of the values k and b must be found, and as can be seen from the data given in the above table, the number of trials is 44, and the values are as follows:
substituting the data into the expressions of k and b in the step 3) to obtain
k＝0.079696；
b＝0.471367
Then a fitted linear equation is obtained as
yi＝0.079696xi+0.471367；
Then, each input value x is divided intoiThe numerical values of all points of the theoretically fitted straight line are obtained by substituting the formula,
| xi | 0 | 10 | 20 | 30 | 40 | 50 |
| yi | 0.471367 | 1.268327 | 2.065287 | 2.862247 | 3.659207 | 4.456167 |
sequentially finding out the deviations of the calibration values from the corresponding point values of the theoretical fitting straight line to be 0.001258, 0.000452, 0.001037, 0.000622, 0.000043 and 0.001833, and using a nonlinear error formula e of the sensorf
The magnitude is typically expressed in terms of relative error, the corresponding maximum deviation being compared (%) to the output value at the full scale (F.S.) of the sensor.
In the formula: e.g. of the typefIs a non-linear error, i.e., linearity; Δ max is the maximum deviation between the output mean and the theoretical value
Delta F.S. is the average value of the full-scale output of the sensor
The non-linearity error of this sensor is:
it will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are intended to be included within the scope of the invention as defined in the appended claims.
Claims (2)
1. A method for determining the linearity of a parachute opening force sensor is characterized by comprising the following steps:
1) obtain parachute opening force sensor's calibration data, include: measured force value xiAnd electrical output yi(ii) a Wherein i is 1,2,3, … …, n;
2) the following parameters were calculated from the calibration test data:
∑xi＝x1+x2+...+xn；
∑yi＝y1+y2+...+yn；
∑xiyi＝x1y1+x2y2+...+xnyn；
∑x2i＝x1 2+x2 2+x3 2+...+xn 2；
3) determining a fitted linear equation for a parachute force cell from the parameters
y＝kx+b；
Wherein the content of the first and second substances,
4) each input value xiSubstituting the fitting linear equation in the step 3) to obtain numerical values of all points of a theoretical fitting linear line, and sequentially finding out the deviation between the calibration data value and the corresponding point value of the theoretical fitting linear line to obtain the maximum deviation;
5) and completing linear calculation according to the maximum deviation and the full range of the sensor.
2. The method for determining the linearity of a parachute opening force sensor according to claim 1, wherein n is equal to or greater than 40.
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| CN202011363385.XA CN112611485A (en) | 2020-11-27 | 2020-11-27 | Method for determining linearity of parachute opening force sensor |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101793532A (en) * | 2010-03-25 | 2010-08-04 | 合肥工业大学 | Error detection method of output voltage values of multi-batch eddy current sensor |
| CN105092132A (en) * | 2015-09-18 | 2015-11-25 | 航宇救生装备有限公司 | Escape parachute dynamic parachute opening force multi-direction test method and device |
| CN106443543A (en) * | 2016-09-18 | 2017-02-22 | 中国科学院上海应用物理研究所 | Linearity testing method for current sensor |
| CN107643095A (en) * | 2017-08-23 | 2018-01-30 | 宁波中车时代传感技术有限公司 | A kind of calibration method of sensor chip and the chip calibration programmable device of application this method |
| CN111024306A (en) * | 2019-10-15 | 2020-04-17 | 长沙理工大学 | Dynamic calibration method for linearity of force sensor for measuring collision force |
-
2020
- 2020-11-27 CN CN202011363385.XA patent/CN112611485A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101793532A (en) * | 2010-03-25 | 2010-08-04 | 合肥工业大学 | Error detection method of output voltage values of multi-batch eddy current sensor |
| CN105092132A (en) * | 2015-09-18 | 2015-11-25 | 航宇救生装备有限公司 | Escape parachute dynamic parachute opening force multi-direction test method and device |
| CN106443543A (en) * | 2016-09-18 | 2017-02-22 | 中国科学院上海应用物理研究所 | Linearity testing method for current sensor |
| CN107643095A (en) * | 2017-08-23 | 2018-01-30 | 宁波中车时代传感技术有限公司 | A kind of calibration method of sensor chip and the chip calibration programmable device of application this method |
| CN111024306A (en) * | 2019-10-15 | 2020-04-17 | 长沙理工大学 | Dynamic calibration method for linearity of force sensor for measuring collision force |
Non-Patent Citations (2)
| Title |
|---|
| 谭定忠: "《传感器与测试技术》", 31 July 2002, 北京：中央广播电视大学出版社 第一版 * |
| 马敏毓: "用于重装空投的张力传感器研制", 《中国优秀硕博士学位论文全文数据库（硕士）信息科技辑》 * |
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Application publication date: 20210406 |